Airworthiness Directives; Bombardier, Inc., Airplanes, 17719-17723 [2024-05191]
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Federal Register / Vol. 89, No. 49 / Tuesday, March 12, 2024 / Rules and Regulations
locations on Model A350 airplanes. The
unsafe condition, if not addressed, could lead
to lavatory module detachment, with
consequent injury to cabin crew and
passengers, and possibly result in reduced
evacuation capacity from the airplane in case
of an emergency.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, European Union Aviation
Safety Agency (EASA) AD 2023–0102, dated
May 17, 2023 (EASA AD 2023–0102).
(h) Exceptions to EASA AD 2023–0102
(1) Where EASA AD 2023–0102 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) This AD does not adopt the ‘‘Remarks’’
section of EASA AD 2023–0102.
(3) Paragraph (4) of EASA AD 2023–0102
specifies to report inspection results to
Airbus within a certain compliance time. For
this AD, report inspection results at the
applicable time specified in paragraph
(h)(3)(i) or (ii) of this AD.
(i) For each inspection done on or after the
effective date of this AD: Submit the report
within 30 days after the inspection.
(ii) For any inspection done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
(4) Where paragraph (2) of EASA AD 2023–
0102 specifies ‘‘any discrepancy, as defined
in the SB, is detected,’’ this AD requires
replacing those words with ‘‘any corrosion
and other damage is detected.’’
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(i) No Requirement for Return of Parts
Although the service information
referenced in EASA AD 2023–0102 specifies
to return parts to the manufacturer, this AD
does not include that requirement.
(j) Additional AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Validation Branch, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or
responsible Flight Standards Office, as
appropriate. If sending information directly
to the International Validation Branch, send
it to the attention of the person identified in
paragraph (k) of this AD. Information may be
emailed to: 9-AVS-AIR-730-AMOC@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the responsible Flight Standards Office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, International Validation
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Branch, FAA; or EASA; or Airbus SAS’s
EASA Design Organization Approval (DOA).
If approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Required for Compliance (RC): Except
as required by paragraph (j)(2) of this AD, if
any service information contains procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(k) Additional Information
For more information about this AD,
contact Dat Le, Aviation Safety Engineer,
FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 516–228–
7317; email dat.v.le@faa.gov.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency
(EASA) AD 2023–0102, dated May 17, 2023.
(ii) [Reserved]
(3) For EASA AD 2023–0102, contact
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; website
easa.europa.eu. You may find this EASA AD
on the EASA website at ad.easa.europa.eu.
(4) You may view this material at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195.
(5) You may view this material at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
visit www.archives.gov/federal-register/cfr/
ibr-locationsoremailfr.inspection@nara.gov.
Issued on February 6, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2024–05190 Filed 3–11–24; 8:45 am]
BILLING CODE 4910–13–P
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17719
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2023–2001; Project
Identifier MCAI–2023–00666–T; Amendment
39–22676; AD 2024–03–06]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2021–20–
13, which applied to certain
Bombardier, Inc., Model CL–600–2B16
(604 Variant) airplanes. AD 2021–20–13
required repetitive lubrication and
repetitive detailed visual inspections
(DVI) and non-destructive test (NDT)
inspections of the main landing gear
(MLG) shock strut lower pins, and
replacement if necessary. This AD
continues to require the lubrication and
inspections specified in AD 2021–20–13
until the MLG shock strut assembly is
modified by replacing the trailing arm
bushing and installing new dynamic
joint components. This AD was
prompted by a new design solution for
this potential failure of the shock strut
lower pin. The FAA is issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective April 16,
2024.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of April 16, 2024.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of November 18, 2021 (86 FR
57033, October 14, 2021).
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2023–2001; or in person at
Docket Operations between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this final rule, the mandatory
continuing airworthiness information
(MCAI), any comments received, and
other information. The address for
Docket Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
Material Incorporated by Reference:
• For service information identified
in this final rule, contact Bombardier,
SUMMARY:
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Inc., 200 Coˆte-Vertu Road West, Dorval,
Que´bec H4S 2A3, Canada; North
America toll-free telephone 1–866–538–
1247 or direct-dial telephone 1–514–
855–2999; email ac.yul@
aero.bombardier.com; website
bombardier.com.
• You may view this service
information at the FAA, Airworthiness
Products Section, Operational Safety
Branch, 2200 South 216th Street, Des
Moines, WA. For information on the
availability of this material at the FAA,
call 206–231–3195. It is also available at
regulations.gov under Docket No. FAA–
2023–2001.
FOR FURTHER INFORMATION CONTACT:
Gabriel Kim, Aviation Safety Engineer,
FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 516–
228–7300; email 9-avs-nyaco-cos@
faa.gov.
inspections specified in AD 2021–20–13
until the MLG shock strut assembly is
modified by replacing the trailing arm
bushing and installing new dynamic
joint components. The FAA is issuing
this AD to address cracking of the MLG
shock strut lower pin. The unsafe
condition, if not addressed, could result
in structural failure of one or both MLG.
You may examine the MCAI in the
AD docket at regulations.gov under
Docket No. FAA–2023–2001.
SUPPLEMENTARY INFORMATION:
Request To Update the Service
Information to the Latest Revision and
Provide Credit
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Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2021–20–13,
Amendment 39–21751 (86 FR 57033,
October 14, 2021) (AD 2021–20–13). AD
2021–20–13 applied to certain
Bombardier, Inc., Model CL–600–2B16
(604 Variant) airplanes. AD 2021–20–13
required repetitive lubrication and
repetitive DVI and NDT inspections of
the MLG shock strut lower pins, and
replacement if necessary. The FAA
issued AD 2021–20–13 to correct an
unsafe condition identified as cracking
of the MLG shock strut lower pin part
number 19146–3.
The NPRM published in the Federal
Register on October 25, 2023 (88 FR
73265). The NPRM was prompted by
AD CF–2023–32, dated May 9, 2023,
issued by Transport Canada, which is
the aviation authority for Canada
(Transport Canada AD CF–2023–32)
(also referred to as the MCAI). The
MCAI states there is a new design
solution for this potential failure of the
shock strut lower pin, which involves
replacing the training arm bushings at
the attachment and reassembly of the
MLG shock strut assembly to training
arm assembly joint with new dynamic
joint components. As a result, the MCAI
requires this new design as terminating
action for the requirements of Transport
Canada AD CF–2020–54R1.
In the NPRM, the FAA proposed to
continue to require the lubrication and
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Discussion of Final Airworthiness
Directive
Comments
The FAA received comments from
three commenters, including Executive
Jet Management, Inc., NetJets, and
Boeing. The following presents the
comments received on the NPRM and
the FAA’s response to each comment.
Executive Jet Management, Inc.
NetJets, and Boeing requested the FAA
revise the proposed AD to allow using
Bombardier Service Bulletin 604–32–
031 Revision 01, dated March 17, 2023;
Bombardier Service Bulletin 605–32–
008 Revision 01, dated March 17, 2023;
and Bombardier Service Bulletin 650–
32–005 Revision 01, dated March 17,
2023. NetJets also requested that the
proposed AD be revised to add credit for
using the original issues of the service
information.
The FAA agrees to update this final
rule to reference Bombardier Service
Bulletin 604–32–031 Revision 01, dated
March 17, 2023; Bombardier Service
Bulletin 605–32–008 Revision 01, dated
March 17, 2023; and Bombardier
Service Bulletin 650–32–005 Revision
01, dated March 17, 2023, which
include minor changes that do not affect
the substantive requirements proposed
in the NPRM. The FAA has revised this
AD to reflect the updated service
bulletins. The FAA has also added
paragraph (n) of this AD to provide
credit for the original issues of the
applicable service bulletins, and
redesignated subsequent paragraphs
accordingly.
Conclusion
This product has been approved by
the aviation authority of another
country and is approved for operation in
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the United States. Pursuant to the FAA’s
bilateral agreement with this State of
Design Authority, it has notified the
FAA of the unsafe condition described
in the MCAI referenced above. The FAA
reviewed the relevant data, considered
the comments received, and determined
that air safety requires adopting this AD
as proposed. Accordingly, the FAA is
issuing this AD to address the unsafe
condition on this product. Except for
minor editorial changes, and any other
changes described previously, this AD is
adopted as proposed in the NPRM.
None of the changes will increase the
economic burden on any operator.
Related Service Information Under 1
CFR Part 51
The FAA reviewed the following
Bombardier service information:
• Service Bulletin 604–32–031,
Revision 01, dated March 17, 2023.
• Service Bulletin 605–32–008,
Revision 01, dated March 17, 2023.
• Service Bulletin 650–32–005,
Revision 01, dated March 17, 2023.
This service information contains
procedures for disassembling the leftand right-hand MLG shock strut and
trailing arm joint, replacing the trailing
arm bushings at the attachment, and reassembling the joint with new dynamic
joint components. These documents are
distinct since they apply to different
airplane configurations.
This AD also requires the following
Bombardier service information, which
the Director of the Federal Register
approved for incorporation by reference
as of November 18, 2021 (86 FR 57033,
October 14, 2021):
• Service Bulletin 604–32–030, dated
June 30, 2020.
• Service Bulletin 605–32–007, dated
June 30, 2020.
• Service Bulletin 650–32–004, dated
June 30, 2020.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD
affects 433 airplanes of U.S. registry.
The FAA estimates the following
costs to comply with this AD:
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ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
Lubrication and inspections (retained
actions from AD 2021–20–13).
Modification and testing (new actions)
Parts cost
Cost on U.S.
operators
Cost per product
7 work-hours × $85 per hour = $595
$0
$595 per cycle ...........
$257,635 per cycle.
9 work-hours × $85 per hour = $765
2,435
$3,200 ........................
$1,385,600.
The FAA estimates the following
costs to do any necessary on-condition
replacement that would be required
based on the results of the repetitive
inspections. The FAA has no way of
determining the number of aircraft that
might need this on-condition action:
ESTIMATED COSTS OF ON-CONDITION REPLACEMENT
Labor cost
Parts cost
Cost per
product
6 work-hours × $85 per hour = $510 ......................................................................................................................
$2,435
$2,945
Authority for This Rulemaking
List of Subjects in 14 CFR Part 39
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701: General requirements. Under
that section, Congress charges the FAA
with promoting safe flight of civil
aircraft in air commerce by prescribing
regulations for practices, methods, and
procedures the Administrator finds
necessary for safety in air commerce.
This regulation is within the scope of
that authority because it addresses an
unsafe condition that is likely to exist or
develop on products identified in this
rulemaking action.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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Regulatory Findings
The FAA determined that this AD
will not have federalism implications
under Executive Order 13132. This AD
will not have a substantial direct effect
on the States, on the relationship
between the national government and
the States, or on the distribution of
power and responsibilities among the
various levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Will not affect intrastate aviation
in Alaska, and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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The Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive
2021–20–13, Amendment 39–21751 (86
FR 57033, October 14, 2021); and
■ b. Adding the following new
Airworthiness Directive:
■
■
2024–03–06 Bombardier, Inc: Amendment
39–22676; Docket No. FAA–2023–2001;
Project Identifier MCAI–2023–00666–T.
(a) Effective Date
This airworthiness directive (AD) is
effective April 16, 2024.
(b) Affected ADs
This AD replaces AD 2021–20–13,
Amendment 39–21751 (86 FR 57033, October
14, 2021) (AD 2021–20–13).
(c) Applicability
This AD applies to Bombardier, Inc.,
Model CL–600–2B16 (604 Variant) airplanes,
serial numbers (S/N) 5301 through 5665
inclusive, 5701 through 5988 inclusive, and
6050 through 6188 inclusive, certificated in
any category.
(d) Subject
Air Transport Association (ATA) of
America Code: 32, Landing gear.
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(e) Reason
This AD was prompted by reports of
cracking of the main landing gear (MLG)
shock strut lower pin. The FAA is issuing
this AD to address cracking of the MLG shock
strut lower pin. The unsafe condition, if not
addressed, could result in structural failure
of one or both MLG.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Repetitive Lubrication, With
Revised Applicability
This paragraph restates the requirements of
paragraph (g) of AD 2021–20–13, with
revised applicability. Within 200 flight hours
(FH) or 12 months after November 18, 2021
(the effective date of AD 2021–20–13),
whichever occurs first, lubricate the left-hand
(LH) and right-hand (RH) MLG shock strut
lower pins having part number (P/N) 19146–
3, in accordance with paragraph 2.B., ‘‘Part
A,’’ of the Accomplishment Instructions of
the applicable service bulletin, as specified
in paragraphs (g)(1) through (3) of this AD.
Repeat thereafter at intervals not to exceed
200 FH or 12 months, whichever occurs first.
(1) For airplanes having S/N 5301 through
5665 inclusive: Bombardier Service Bulletin
604–32–030, dated June 30, 2020.
(2) For airplanes having S/N 5701 through
5988 inclusive: Bombardier Service Bulletin
605–32–007, dated June 30, 2020.
(3) For airplanes having S/N 6050 through
6188 inclusive: Bombardier Service Bulletin
650–32–004, dated June 30, 2020.
(h) Retained Detailed Visual Inspections
(DVI), With No Changes
This paragraph restates the requirements of
paragraph (h) of AD 2021–20–13, with no
changes. At the applicable compliance time
specified in paragraphs (h)(1) through (3) of
this AD, perform the DVI for cracking and
damage of the LH and RH MLG shock strut
lower pins having part number (P/N) 19146–
3, in accordance with paragraph 2.C., ‘‘Part
B,’’ of the Accomplishment Instructions of
the applicable service bulletin, as specified
in paragraphs (g)(1) through (3) of this AD.
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Repeat thereafter at intervals not to exceed
400 FH or 24 months, whichever occurs first.
If the DVI coincides with a non-destructive
testing (NDT) inspection required by
paragraph (i) of this AD, the NDT inspection
supersedes the DVI for that interval only. If
the accumulated flight cycles (FC) of the
MLG shock strut lower pin are not known,
use the related MLG assembly accumulated
FC to determine when to accomplish the
actions required by this paragraph.
(1) For airplanes with an original
airworthiness certificate or original export
certificate of airworthiness issued on or
before November 18, 2021 (the effective date
of AD 2021–20–13) and on which an MLG
shock strut lower pin has accumulated fewer
than 600 total FC on the pin as of November
18, 2021: Before the accumulation of 750
total FC on the pin.
(2) For airplanes with an original
airworthiness certificate or original export
certificate of airworthiness issued on or
before November 18, 2021 (the effective date
of AD 2021–20–13) and on which an MLG
shock strut lower pin has accumulated 600
total FC or more on the pin as of November
18, 2021: Within 150 FC after November 18,
2021.
(3) For airplanes with an original
airworthiness certificate or original export
certificate of airworthiness issued after
November 18, 2021 (the effective date of AD
2021–20–13): Before the accumulation of 750
total FC.
(i) Retained NDT Inspection, With No
Changes
This paragraph restates the requirements of
paragraph (i) of AD 2021–20–13, with no
changes. At the applicable compliance time
specified in paragraphs (i)(1) through (4) of
this AD: Perform the NDT inspection for
cracking and damage of the LH and RH MLG
shock strut lower pins having P/N 19146–3,
in accordance with paragraph 2.D., ‘‘Part C,’’
of the Accomplishment Instructions of the
applicable service bulletin, as specified in
paragraphs (g)(1) through (3) of this AD.
Repeat thereafter at intervals not to exceed
900 FC. If the accumulated FC of the MLG
shock strut lower pin is not known, use the
related MLG assembly accumulated FC to
determine when to accomplish the actions
required by this paragraph.
(1) For airplanes with an original
airworthiness certificate or original export
certificate of airworthiness issued on or
before November 18, 2021 (the effective date
of AD 2021–20–13) and on which an MLG
shock strut lower pin has accumulated fewer
than 1,200 total FC on the pin as of
November 18, 2021: Before the accumulation
of 1,500 total FC on the pin.
(2) For airplanes with an original
airworthiness certificate or original export
certificate of airworthiness issued on or
before November 18, 2021 (the effective date
of AD 2021–20–13) and on which an MLG
shock strut lower pin has accumulated 1,200
total FC or more but fewer than 2,000 total
FC on the pin as of November 18, 2021:
Within 300 FC after November 18, 2021, or
before the accumulation of 2,200 total FC on
the pin, whichever occurs first.
(3) For airplanes with an original
airworthiness certificate or original export
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certificate of airworthiness issued on or
before November 18, 2021 (the effective date
of AD 2021–20–13) and on which an MLG
shock strut lower pin has accumulated 2,000
total FC or more on the pin as of November
18, 2021: Within 200 FC after November 18,
2021.
(4) For airplanes with an original
airworthiness certificate or original export
certificate of airworthiness issued after
November 18, 2021 (the effective date of AD
2021–20–13): Before the accumulation of
1,500 total FC.
(j) Retained Replacement, With No Changes
This paragraph restates the requirements of
paragraph (j) of AD 2021–20–13, with no
changes. If, during any inspection required
by this AD, any crack or damage of the MLG
shock strut lower pin is detected, before
further flight, replace the affected MLG shock
strut lower pin with a new part in accordance
with paragraph 2.E., ‘‘Part D,’’ of the
Accomplishment Instructions of the
applicable service bulletin, as specified in
paragraphs (g)(1) through (3) of this AD.
(k) New Requirement of This AD:
Modification
Within 60 months from the effective date
of this AD, modify the LH and RH MLG
assembly in accordance with paragraph 2.B.
of the Accomplishment Instructions of the
applicable service bulletin, as specified in
paragraphs (k)(1) through (3) of this AD.
(1) For airplanes having S/N 5301 through
5665 inclusive: Bombardier Service Bulletin
604–32–031, Revision 01, dated March 17,
2023.
(2) For airplanes having S/N 5701 through
5988 inclusive: Bombardier Service Bulletin
605–32–008, Revision 01, dated March 17,
2023.
(3) For airplanes having S/N 6050 through
6188 inclusive: Bombardier Service Bulletin
650–32–005, Revision 01, dated March 17,
2023.
(l) New Requirement of the AD: Testing
Before further flight after completing the
actions required by paragraph (k) of this AD,
perform the testing of the MLG shock strut
assembly to trailing arm assembly joint in
accordance with paragraph 2.C. of the
Accomplishment Instructions of the
applicable service bulletin, as specified in
paragraphs (k)(1) through (3) of this AD.
(m) Terminating Action
Modifying and testing an airplane as
required by paragraphs (k) and (l) of this AD
terminates the initial and repetitive
lubrication and inspections required by
paragraphs (g), (h), and (i) of this AD for that
airplane.
(n) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (k) and (l) of this AD,
if those actions were performed before the
effective date of this AD using Bombardier
Service Bulletin 604–32–031, dated
December 29, 2022; Bombardier Service
Bulletin 605–32–008, dated December 29,
2022; or Bombardier Service Bulletin 650–
32–005, dated December 29, 2022.
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(o) Additional AD Provisions
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Validation Branch, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or
responsible Flight Standards Office, as
appropriate. If sending information directly
to the manager of the International Validation
Branch, mail it to the address identified in
paragraph (p)(2) of this AD or email to: 9AVS-AIR-730-AMOC@faa.gov. If mailing
information, also submit information by
email. Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the responsible Flight Standards Office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, International Validation
Branch, FAA; or Transport Canada; or
Bombardier, Inc.’s Transport Canada Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
(p) Additional Information
(1) Refer to Transport Canada AD CF–
2023–32, dated May 9, 2023, for related
information. This Transport Canada AD may
be found in the AD docket at regulations.gov
under Docket No. FAA–2023–2001.
(2) For more information about this AD,
contact Gabriel Kim, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite
410, Westbury, NY 11590; telephone 516–
228–7300; email 9-avs-nyaco-cos@faa.gov.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (q)(5) and (6) of this AD.
(q) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on April 16, 2024.
(i) Bombardier Service Bulletin 604–32–
031, Revision 01, dated March 17, 2023.
(ii) Bombardier Service Bulletin 605–32–
008, Revision 01, dated March 17, 2023.
(iii) Bombardier Service Bulletin 650–32–
005, Revision 01, dated March 17, 2023.
(4) The following service information was
approved for IBR on November 18, 2021 (86
FR 57033, October 14, 2021).
(i) Bombardier Service Bulletin 604–32–
030, dated June 30, 2020.
(ii) Bombardier Service Bulletin 605–32–
007, dated June 30, 2020.
(iii) Bombardier Service Bulletin 650–32–
004, dated June 30, 2020.
(5) For service information identified in
this AD, contact Bombardier, Inc., 200 CoˆteVertu Road West, Dorval, Que´bec H4S 2A3,
Canada; North America toll-free telephone 1–
E:\FR\FM\12MRR1.SGM
12MRR1
Federal Register / Vol. 89, No. 49 / Tuesday, March 12, 2024 / Rules and Regulations
866–538–1247 or direct-dial telephone 1–
514–855–2999; email ac.yul@
aero.bombardier.com; website
bombardier.com.
(6) You may view this material at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th Street, Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195.
(7) You may view this material at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
visit www.archives.gov/federal-register/cfr/
ibr-locationsoremailfr.inspection@nara.gov.
Issued on February 7, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2024–05191 Filed 3–11–24; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2023–2230; Project
Identifier MCAI–2023–00861–T; Amendment
39–22677; AD 2024–03–07]
RIN 2120–AA64
Airworthiness Directives; Deutsche
Aircraft GmbH (Type Certificate
Previously Held by 328 Support
Services GmbH; AvCraft Aerospace
GmbH; Fairchild Dornier GmbH;
Dornier Luftahrt GmbH) Airplanes
Background
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
Deutsche Aircraft GmbH Model 328–100
and 328–300 airplanes. This AD was
prompted by operator reports of worn
and ruptured bonding straps inside the
feeder wing tanks and in both outer and
inner wing tanks. This AD requires a
one-time detailed inspection of each
affected part, and applicable corrective
actions, as specified in a European
Union Aviation Safety Agency (EASA)
AD, which is incorporated by reference.
The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective April 16,
2024.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 16, 2024.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
khammond on DSKJM1Z7X2PROD with RULES
SUMMARY:
VerDate Sep<11>2014
16:07 Mar 11, 2024
Jkt 262001
No. FAA–2023–2230; or in person at
Docket Operations between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this final rule, the mandatory
continuing airworthiness information
(MCAI), any comments received, and
other information. The address for
Docket Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
Material Incorporated by Reference:
• For EASA material incorporated by
reference in this AD, contact EASA,
Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221
8999 000; email ADs@easa.europa.eu;
website easa.europa.eu. You may find
this material on the EASA website at
ad.easa.europa.eu.
• You may view this material at the
FAA, Airworthiness Products Section,
Operational Safety Branch, 2200 South
216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available in the AD docket at
regulations.gov under Docket No. FAA–
2023–2230.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590;
telephone 206–231–3228; email
Todd.Thompson@faa.gov.
SUPPLEMENTARY INFORMATION:
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Deutsche Aircraft GmbH
(Type Certificate previously held by 328
Support Services GmbH; AvCraft
Aerospace GmbH; Fairchild Dornier
GmbH; Dornier Luftfahrt GmbH) Model
328–100 and 328–300 airplanes. The
NPRM published in the Federal
Register on December 6, 2023 (88 FR
84764). The NPRM was prompted by
AD 2023–0137, dated July 12, 2023
(EASA AD 2023–0137) (also referred to
as the MCAI), issued by EASA, which
is the Technical Agent for the Member
States of the European Union. The
MCAI states that operators reported
findings of damaged affected parts. The
extent of the detected damage of the
affected parts did not ensure that
appropriately low electrical impedance
is obtained and maintained through the
affected bonding path. The unsafe
condition, if not detected and corrected,
could lead to the loss of bonding
function and, in combination with a
lightning strike, create a source of
PO 00000
Frm 00031
Fmt 4700
Sfmt 4700
17723
ignition in a fuel tank, possibly resulting
in a fire or explosion.
In the NPRM, the FAA proposed to
require a one-time detailed inspection of
each affected part, and applicable
corrective actions, as specified in EASA
AD 2023–0137. The FAA is issuing this
AD to address the unsafe condition on
these products.
You may examine the MCAI in the
AD docket at regulations.gov under
Docket No. FAA–2023–2230.
Discussion of Final Airworthiness
Directive
Comments
The FAA received no comments on
the NPRM or on the determination of
the cost to the public.
Conclusion
This product has been approved by
the aviation authority of another
country and is approved for operation in
the United States. Pursuant to the FAA’s
bilateral agreement with this State of
Design Authority, it has notified the
FAA of the unsafe condition described
in the MCAI referenced above. The FAA
reviewed the relevant data and
determined that air safety requires
adopting this AD as proposed.
Accordingly, the FAA is issuing this AD
to address the unsafe condition on this
product. Except for minor editorial
changes, this AD is adopted as proposed
in the NPRM. None of the changes will
increase the economic burden on any
operator.
Related Service Information Under 1
CFR Part 51
EASA AD 2023–0137 specifies
procedures for a one-time detailed
inspection of each affected part for worn
and ruptured bonding straps, and
applicable corrective actions (replacing
the affected parts). This material is
reasonably available because the
interested parties have access to it
through their normal course of business
or by the means identified in the
ADDRESSES section.
Interim Action
The FAA considers that this AD is an
interim action. If final action is later
identified, the FAA might consider
further rulemaking then.
Costs of Compliance
The FAA estimates that this AD
affects 35 airplanes of U.S. registry. The
FAA estimates the following costs to
comply with this AD:
E:\FR\FM\12MRR1.SGM
12MRR1
]]>Agencies
[Federal Register Volume 89, Number 49 (Tuesday, March 12, 2024)]
[Rules and Regulations]
[Pages 17719-17723]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-05191]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-2001; Project Identifier MCAI-2023-00666-T;
Amendment 39-22676; AD 2024-03-06]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc., Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2021-20-
13, which applied to certain Bombardier, Inc., Model CL-600-2B16 (604
Variant) airplanes. AD 2021-20-13 required repetitive lubrication and
repetitive detailed visual inspections (DVI) and non-destructive test
(NDT) inspections of the main landing gear (MLG) shock strut lower
pins, and replacement if necessary. This AD continues to require the
lubrication and inspections specified in AD 2021-20-13 until the MLG
shock strut assembly is modified by replacing the trailing arm bushing
and installing new dynamic joint components. This AD was prompted by a
new design solution for this potential failure of the shock strut lower
pin. The FAA is issuing this AD to address the unsafe condition on
these products.
DATES: This AD is effective April 16, 2024.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 16,
2024.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
November 18, 2021 (86 FR 57033, October 14, 2021).
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2023-2001; or in person at Docket Operations between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this final rule, the mandatory continuing airworthiness
information (MCAI), any comments received, and other information. The
address for Docket Operations is U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE, Washington, DC 20590.
Material Incorporated by Reference:
For service information identified in this final rule,
contact Bombardier,
[[Page 17720]]
Inc., 200 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec H4S 2A3,
Canada; North America toll-free telephone 1-866-538-1247 or direct-dial
telephone 1-514-855-2999; email bombardier.com">ac.yul@aero.bombardier.com; website
bombardier.com.
You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 2200 South
216th Street, Des Moines, WA. For information on the availability of
this material at the FAA, call 206-231-3195. It is also available at
regulations.gov under Docket No. FAA-2023-2001.
FOR FURTHER INFORMATION CONTACT: Gabriel Kim, Aviation Safety Engineer,
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-
228-7300; email [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2021-20-13, Amendment 39-21751 (86 FR
57033, October 14, 2021) (AD 2021-20-13). AD 2021-20-13 applied to
certain Bombardier, Inc., Model CL-600-2B16 (604 Variant) airplanes. AD
2021-20-13 required repetitive lubrication and repetitive DVI and NDT
inspections of the MLG shock strut lower pins, and replacement if
necessary. The FAA issued AD 2021-20-13 to correct an unsafe condition
identified as cracking of the MLG shock strut lower pin part number
19146-3.
The NPRM published in the Federal Register on October 25, 2023 (88
FR 73265). The NPRM was prompted by AD CF-2023-32, dated May 9, 2023,
issued by Transport Canada, which is the aviation authority for Canada
(Transport Canada AD CF-2023-32) (also referred to as the MCAI). The
MCAI states there is a new design solution for this potential failure
of the shock strut lower pin, which involves replacing the training arm
bushings at the attachment and reassembly of the MLG shock strut
assembly to training arm assembly joint with new dynamic joint
components. As a result, the MCAI requires this new design as
terminating action for the requirements of Transport Canada AD CF-2020-
54R1.
In the NPRM, the FAA proposed to continue to require the
lubrication and inspections specified in AD 2021-20-13 until the MLG
shock strut assembly is modified by replacing the trailing arm bushing
and installing new dynamic joint components. The FAA is issuing this AD
to address cracking of the MLG shock strut lower pin. The unsafe
condition, if not addressed, could result in structural failure of one
or both MLG.
You may examine the MCAI in the AD docket at regulations.gov under
Docket No. FAA-2023-2001.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from three commenters, including
Executive Jet Management, Inc., NetJets, and Boeing. The following
presents the comments received on the NPRM and the FAA's response to
each comment.
Request To Update the Service Information to the Latest Revision and
Provide Credit
Executive Jet Management, Inc. NetJets, and Boeing requested the
FAA revise the proposed AD to allow using Bombardier Service Bulletin
604-32-031 Revision 01, dated March 17, 2023; Bombardier Service
Bulletin 605-32-008 Revision 01, dated March 17, 2023; and Bombardier
Service Bulletin 650-32-005 Revision 01, dated March 17, 2023. NetJets
also requested that the proposed AD be revised to add credit for using
the original issues of the service information.
The FAA agrees to update this final rule to reference Bombardier
Service Bulletin 604-32-031 Revision 01, dated March 17, 2023;
Bombardier Service Bulletin 605-32-008 Revision 01, dated March 17,
2023; and Bombardier Service Bulletin 650-32-005 Revision 01, dated
March 17, 2023, which include minor changes that do not affect the
substantive requirements proposed in the NPRM. The FAA has revised this
AD to reflect the updated service bulletins. The FAA has also added
paragraph (n) of this AD to provide credit for the original issues of
the applicable service bulletins, and redesignated subsequent
paragraphs accordingly.
Conclusion
This product has been approved by the aviation authority of another
country and is approved for operation in the United States. Pursuant to
the FAA's bilateral agreement with this State of Design Authority, it
has notified the FAA of the unsafe condition described in the MCAI
referenced above. The FAA reviewed the relevant data, considered the
comments received, and determined that air safety requires adopting
this AD as proposed. Accordingly, the FAA is issuing this AD to address
the unsafe condition on this product. Except for minor editorial
changes, and any other changes described previously, this AD is adopted
as proposed in the NPRM. None of the changes will increase the economic
burden on any operator.
Related Service Information Under 1 CFR Part 51
The FAA reviewed the following Bombardier service information:
Service Bulletin 604-32-031, Revision 01, dated March 17,
2023.
Service Bulletin 605-32-008, Revision 01, dated March 17,
2023.
Service Bulletin 650-32-005, Revision 01, dated March 17,
2023.
This service information contains procedures for disassembling the
left- and right-hand MLG shock strut and trailing arm joint, replacing
the trailing arm bushings at the attachment, and re-assembling the
joint with new dynamic joint components. These documents are distinct
since they apply to different airplane configurations.
This AD also requires the following Bombardier service information,
which the Director of the Federal Register approved for incorporation
by reference as of November 18, 2021 (86 FR 57033, October 14, 2021):
Service Bulletin 604-32-030, dated June 30, 2020.
Service Bulletin 605-32-007, dated June 30, 2020.
Service Bulletin 650-32-004, dated June 30, 2020.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD affects 433 airplanes of U.S.
registry.
The FAA estimates the following costs to comply with this AD:
[[Page 17721]]
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Lubrication and inspections 7 work-hours x $85 $0 $595 per cycle..... $257,635 per cycle.
(retained actions from AD 2021- per hour = $595.
20-13).
Modification and testing (new 9 work-hours x $85 2,435 $3,200............. $1,385,600.
actions). per hour = $765.
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary on-
condition replacement that would be required based on the results of
the repetitive inspections. The FAA has no way of determining the
number of aircraft that might need this on-condition action:
Estimated Costs of On-Condition Replacement
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
------------------------------------------------------------------------
6 work-hours x $85 per hour = $510.... $2,435 $2,945
------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
The FAA determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by:
0
a. Removing Airworthiness Directive 2021-20-13, Amendment 39-21751 (86
FR 57033, October 14, 2021); and
0
b. Adding the following new Airworthiness Directive:
2024-03-06 Bombardier, Inc: Amendment 39-22676; Docket No. FAA-2023-
2001; Project Identifier MCAI-2023-00666-T.
(a) Effective Date
This airworthiness directive (AD) is effective April 16, 2024.
(b) Affected ADs
This AD replaces AD 2021-20-13, Amendment 39-21751 (86 FR 57033,
October 14, 2021) (AD 2021-20-13).
(c) Applicability
This AD applies to Bombardier, Inc., Model CL-600-2B16 (604
Variant) airplanes, serial numbers (S/N) 5301 through 5665
inclusive, 5701 through 5988 inclusive, and 6050 through 6188
inclusive, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code: 32, Landing
gear.
(e) Reason
This AD was prompted by reports of cracking of the main landing
gear (MLG) shock strut lower pin. The FAA is issuing this AD to
address cracking of the MLG shock strut lower pin. The unsafe
condition, if not addressed, could result in structural failure of
one or both MLG.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Repetitive Lubrication, With Revised Applicability
This paragraph restates the requirements of paragraph (g) of AD
2021-20-13, with revised applicability. Within 200 flight hours (FH)
or 12 months after November 18, 2021 (the effective date of AD 2021-
20-13), whichever occurs first, lubricate the left-hand (LH) and
right-hand (RH) MLG shock strut lower pins having part number (P/N)
19146-3, in accordance with paragraph 2.B., ``Part A,'' of the
Accomplishment Instructions of the applicable service bulletin, as
specified in paragraphs (g)(1) through (3) of this AD. Repeat
thereafter at intervals not to exceed 200 FH or 12 months, whichever
occurs first.
(1) For airplanes having S/N 5301 through 5665 inclusive:
Bombardier Service Bulletin 604-32-030, dated June 30, 2020.
(2) For airplanes having S/N 5701 through 5988 inclusive:
Bombardier Service Bulletin 605-32-007, dated June 30, 2020.
(3) For airplanes having S/N 6050 through 6188 inclusive:
Bombardier Service Bulletin 650-32-004, dated June 30, 2020.
(h) Retained Detailed Visual Inspections (DVI), With No Changes
This paragraph restates the requirements of paragraph (h) of AD
2021-20-13, with no changes. At the applicable compliance time
specified in paragraphs (h)(1) through (3) of this AD, perform the
DVI for cracking and damage of the LH and RH MLG shock strut lower
pins having part number (P/N) 19146-3, in accordance with paragraph
2.C., ``Part B,'' of the Accomplishment Instructions of the
applicable service bulletin, as specified in paragraphs (g)(1)
through (3) of this AD.
[[Page 17722]]
Repeat thereafter at intervals not to exceed 400 FH or 24 months,
whichever occurs first. If the DVI coincides with a non-destructive
testing (NDT) inspection required by paragraph (i) of this AD, the
NDT inspection supersedes the DVI for that interval only. If the
accumulated flight cycles (FC) of the MLG shock strut lower pin are
not known, use the related MLG assembly accumulated FC to determine
when to accomplish the actions required by this paragraph.
(1) For airplanes with an original airworthiness certificate or
original export certificate of airworthiness issued on or before
November 18, 2021 (the effective date of AD 2021-20-13) and on which
an MLG shock strut lower pin has accumulated fewer than 600 total FC
on the pin as of November 18, 2021: Before the accumulation of 750
total FC on the pin.
(2) For airplanes with an original airworthiness certificate or
original export certificate of airworthiness issued on or before
November 18, 2021 (the effective date of AD 2021-20-13) and on which
an MLG shock strut lower pin has accumulated 600 total FC or more on
the pin as of November 18, 2021: Within 150 FC after November 18,
2021.
(3) For airplanes with an original airworthiness certificate or
original export certificate of airworthiness issued after November
18, 2021 (the effective date of AD 2021-20-13): Before the
accumulation of 750 total FC.
(i) Retained NDT Inspection, With No Changes
This paragraph restates the requirements of paragraph (i) of AD
2021-20-13, with no changes. At the applicable compliance time
specified in paragraphs (i)(1) through (4) of this AD: Perform the
NDT inspection for cracking and damage of the LH and RH MLG shock
strut lower pins having P/N 19146-3, in accordance with paragraph
2.D., ``Part C,'' of the Accomplishment Instructions of the
applicable service bulletin, as specified in paragraphs (g)(1)
through (3) of this AD. Repeat thereafter at intervals not to exceed
900 FC. If the accumulated FC of the MLG shock strut lower pin is
not known, use the related MLG assembly accumulated FC to determine
when to accomplish the actions required by this paragraph.
(1) For airplanes with an original airworthiness certificate or
original export certificate of airworthiness issued on or before
November 18, 2021 (the effective date of AD 2021-20-13) and on which
an MLG shock strut lower pin has accumulated fewer than 1,200 total
FC on the pin as of November 18, 2021: Before the accumulation of
1,500 total FC on the pin.
(2) For airplanes with an original airworthiness certificate or
original export certificate of airworthiness issued on or before
November 18, 2021 (the effective date of AD 2021-20-13) and on which
an MLG shock strut lower pin has accumulated 1,200 total FC or more
but fewer than 2,000 total FC on the pin as of November 18, 2021:
Within 300 FC after November 18, 2021, or before the accumulation of
2,200 total FC on the pin, whichever occurs first.
(3) For airplanes with an original airworthiness certificate or
original export certificate of airworthiness issued on or before
November 18, 2021 (the effective date of AD 2021-20-13) and on which
an MLG shock strut lower pin has accumulated 2,000 total FC or more
on the pin as of November 18, 2021: Within 200 FC after November 18,
2021.
(4) For airplanes with an original airworthiness certificate or
original export certificate of airworthiness issued after November
18, 2021 (the effective date of AD 2021-20-13): Before the
accumulation of 1,500 total FC.
(j) Retained Replacement, With No Changes
This paragraph restates the requirements of paragraph (j) of AD
2021-20-13, with no changes. If, during any inspection required by
this AD, any crack or damage of the MLG shock strut lower pin is
detected, before further flight, replace the affected MLG shock
strut lower pin with a new part in accordance with paragraph 2.E.,
``Part D,'' of the Accomplishment Instructions of the applicable
service bulletin, as specified in paragraphs (g)(1) through (3) of
this AD.
(k) New Requirement of This AD: Modification
Within 60 months from the effective date of this AD, modify the
LH and RH MLG assembly in accordance with paragraph 2.B. of the
Accomplishment Instructions of the applicable service bulletin, as
specified in paragraphs (k)(1) through (3) of this AD.
(1) For airplanes having S/N 5301 through 5665 inclusive:
Bombardier Service Bulletin 604-32-031, Revision 01, dated March 17,
2023.
(2) For airplanes having S/N 5701 through 5988 inclusive:
Bombardier Service Bulletin 605-32-008, Revision 01, dated March 17,
2023.
(3) For airplanes having S/N 6050 through 6188 inclusive:
Bombardier Service Bulletin 650-32-005, Revision 01, dated March 17,
2023.
(l) New Requirement of the AD: Testing
Before further flight after completing the actions required by
paragraph (k) of this AD, perform the testing of the MLG shock strut
assembly to trailing arm assembly joint in accordance with paragraph
2.C. of the Accomplishment Instructions of the applicable service
bulletin, as specified in paragraphs (k)(1) through (3) of this AD.
(m) Terminating Action
Modifying and testing an airplane as required by paragraphs (k)
and (l) of this AD terminates the initial and repetitive lubrication
and inspections required by paragraphs (g), (h), and (i) of this AD
for that airplane.
(n) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (k) and (l) of this AD, if those actions were performed
before the effective date of this AD using Bombardier Service
Bulletin 604-32-031, dated December 29, 2022; Bombardier Service
Bulletin 605-32-008, dated December 29, 2022; or Bombardier Service
Bulletin 650-32-005, dated December 29, 2022.
(o) Additional AD Provisions
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Validation Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or responsible Flight Standards Office, as
appropriate. If sending information directly to the manager of the
International Validation Branch, mail it to the address identified
in paragraph (p)(2) of this AD or email to: [email protected]. If mailing information, also submit information by
email. Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the responsible Flight Standards Office.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain instructions from a manufacturer, the instructions must be
accomplished using a method approved by the Manager, International
Validation Branch, FAA; or Transport Canada; or Bombardier, Inc.'s
Transport Canada Design Approval Organization (DAO). If approved by
the DAO, the approval must include the DAO-authorized signature.
(p) Additional Information
(1) Refer to Transport Canada AD CF-2023-32, dated May 9, 2023,
for related information. This Transport Canada AD may be found in
the AD docket at regulations.gov under Docket No. FAA-2023-2001.
(2) For more information about this AD, contact Gabriel Kim,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 516-228-7300; email [email protected].
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (q)(5) and (6) of this AD.
(q) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on
April 16, 2024.
(i) Bombardier Service Bulletin 604-32-031, Revision 01, dated
March 17, 2023.
(ii) Bombardier Service Bulletin 605-32-008, Revision 01, dated
March 17, 2023.
(iii) Bombardier Service Bulletin 650-32-005, Revision 01, dated
March 17, 2023.
(4) The following service information was approved for IBR on
November 18, 2021 (86 FR 57033, October 14, 2021).
(i) Bombardier Service Bulletin 604-32-030, dated June 30, 2020.
(ii) Bombardier Service Bulletin 605-32-007, dated June 30,
2020.
(iii) Bombardier Service Bulletin 650-32-004, dated June 30,
2020.
(5) For service information identified in this AD, contact
Bombardier, Inc., 200 C[ocirc]te-Vertu Road West, Dorval,
Qu[eacute]bec H4S 2A3, Canada; North America toll-free telephone 1-
[[Page 17723]]
866-538-1247 or direct-dial telephone 1-514-855-2999; email
bombardier.com">ac.yul@aero.bombardier.com; website bombardier.com.
(6) You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 2200 South 216th
Street, Des Moines, WA. For information on the availability of this
material at the FAA, call 206-231-3195.
(7) You may view this material at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, visit www.archives.gov/federal-register/cfr/[email protected]">www.archives.gov/federal-register/cfr/[email protected].
Issued on February 7, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2024-05191 Filed 3-11-24; 8:45 am]
BILLING CODE 4910-13-P
